Turbine engine with fuel nozzle

Patent metadata

Field	Value
Publication number	US-2025251131-A1
Application number	US-202418613824-A
Country	US
Kind code	A1
Filing date	Mar 22, 2024
Priority date	Dec 21, 2021
Publication date	Aug 7, 2025
Grant date	—

Abstract

An engine can utilize a combustor to combust fuel to drive the engine. A fuel nozzle assembly can supply fuel to the combustor for combustion or ignition of the fuel. The fuel nozzle assembly can include a swirler and a fuel nozzle to supply a mixture of fuel and air for combustion. Increasing efficiency and meeting emission needs can be met with the use of alternative fuels, which combust at higher temperatures or higher speeds than traditional fuels, requiring improved fuel introduction without the occurrence of flame holding or flashback.

First claim

What is claimed is:

1 . A turbine engine comprising:
a compressor section, combustor section, and turbine section in serial flow arrangement, with the combustor section including a fuel nozzle assembly comprising: a fuel nozzle including a fuel passage defining a longitudinal axis, the fuel nozzle terminating at a nozzle tip; a swirler defining a swirler passage about the fuel nozzle, having a forward wall spaced from an aft wall, and having a center wall positioned between the forward wall and the aft wall; a set of vanes provided within the swirler; a lip extending downstream from the center wall relative to a flow direction through the swirler, and the lip terminating at an aft end; and a purge opening extending through the forward wall and exhausting to the swirler passage; wherein the nozzle tip is positioned aft of the aft end of the lip relative to the longitudinal axis.

2 . The turbine engine of claim 1 , wherein the aft end of the lip is positioned forward of the aft wall relative to the longitudinal axis.

3 . The turbine engine of claim 1 , wherein the purge opening is one of a set of purge openings in annular arrangement about the fuel nozzle.

4 . The turbine engine of claim 1 , wherein the purge opening is provided as an annular opening in annular arrangement about the fuel nozzle.

5 . The turbine engine of claim 1 , wherein the purge opening defines a purge axis and wherein the purge opening is arranged such that the purge axis defines an angle relative to the longitudinal axis.

6 . The turbine engine of claim 5 , wherein the angle is between negative ten degrees and sixty degrees.

7 . The turbine engine of claim 5 , wherein the purge opening is oriented to impinge upon the fuel nozzle.

8 . The turbine engine of claim 1 , wherein the purge opening is arranged parallel to the longitudinal axis.

9 . The turbine engine of claim 1 , wherein the purge opening axially overlaps with the lip in a direction parallel to the longitudinal axis.

10 . The turbine engine of claim 1 , wherein the purge opening extends through the forward wall along the fuel nozzle.

11 . The turbine engine of claim 1 , wherein the purge opening includes a semicircular cross-sectional shape.

12 . The turbine engine of claim 1 , further comprising an annular groove arranged within the forward wall between the purge opening and the swirler passage.

13 . The turbine engine of claim 12 , wherein the purge opening is provided as multiple purge openings in stacked arrangement exhausting to the annular groove.

14 . The turbine engine of claim 1 , wherein the swirler passage defines a swirler height as a radial length between the fuel nozzle and the swirler in a direction perpendicular to the longitudinal axis, and wherein the lip height can be between −0.9 times the swirler height to 0.9 times the swirler height.

15 . The turbine engine of claim 14 , wherein a swirler passage length is defined as an axial distance between the lip and the nozzle tip, and wherein the lip height can be between one to six times the swirler passage length.

16 . A fuel nozzle assembly comprising:
a fuel nozzle including a fuel passage defining a longitudinal axis, the fuel nozzle terminating at a nozzle tip; a swirler defining a swirler passage about the fuel nozzle, having a forward wall spaced from an aft wall, and having a center wall positioned between the forward wall and the aft wall; a lip extending downstream from the center wall relative to a flow direction through the swirler, and the lip terminating at an aft end; and a purge opening extending through the forward wall and exhausting to the swirler passage; wherein the nozzle tip is positioned aft of the aft end of the lip relative to the longitudinal axis.

17 . The fuel nozzle assembly of claim 16 , wherein the aft end of the lip is positioned forward of the aft wall relative to the longitudinal axis.

18 . The fuel nozzle assembly of claim 16 , wherein the purge opening defines a purge axis and wherein the purge opening is arranged such that the purge axis defines an angle relative to the longitudinal axis.

19 . The fuel nozzle assembly of claim 18 , wherein the purge axis orients the purge opening to impinge upon the fuel nozzle.

20 . The fuel nozzle assembly of claim 1 , further comprising an annular groove arranged within the forward wall between the purge opening and the swirler passage.

Assignees

• Gen Electric

Inventors

• Naik Pradeep
• Vukanti Perumallu
• Bucaro Michael T
• Vise Steven C
• Patra Ajoy
• Chiranthan R Narasimha
• Giridharan Manampathy G
• Benjamin Michael A
• Cooper Clayton S
• Pachaiappan Dharmaraj

Classifications

• F23R3/286

  having fuel-air premixing devices (F23R3/30 takes precedence) · CPC title

• F23R2900/00002

  Gas turbine combustors adapted for fuels having low heating value [LHV] · CPC title

• F23R3/14 Primary

  by using swirl vanes · CPC title